EP3842618B1 - Improved patch rings and methods of use - Google Patents
Improved patch rings and methods of use Download PDFInfo
- Publication number
- EP3842618B1 EP3842618B1 EP20212534.0A EP20212534A EP3842618B1 EP 3842618 B1 EP3842618 B1 EP 3842618B1 EP 20212534 A EP20212534 A EP 20212534A EP 3842618 B1 EP3842618 B1 EP 3842618B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rabbet
- arm
- extending face
- shaft
- turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
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- 238000003754 machining Methods 0.000 claims description 7
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- 238000002485 combustion reaction Methods 0.000 description 10
- 239000012530 fluid Substances 0.000 description 8
- 230000000712 assembly Effects 0.000 description 6
- 238000000429 assembly Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 125000006850 spacer group Chemical group 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
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- 230000007547 defect Effects 0.000 description 1
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- 230000005611 electricity Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
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- 238000010926 purge Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/04—Shafts or bearings, or assemblies thereof
- F04D29/0405—Shafts or bearings, or assemblies thereof joining shafts, e.g. rigid couplings, quill shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/04—Shafts or bearings, or assemblies thereof
- F04D29/043—Shafts
- F04D29/044—Arrangements for joining or assembling shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
- F04D29/054—Arrangements for joining or assembling shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/02—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for connecting two abutting shafts or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/60—Shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2250/00—Manufacturing; Assembly
- F16D2250/0084—Assembly or disassembly
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2300/00—Special features for couplings or clutches
Definitions
- the present disclosure relates generally to improved patch rings and associated methods.
- the invention relates to improved patch rings for use in turbomachine marriage joints.
- a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section.
- the compressor section progressively increases the pressure of a working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section.
- the compressed working fluid and a fuel e.g., natural gas
- the combustion gases flow from the combustion section into the turbine section where they expand to produce work.
- expansion of the combustion gases in the turbine section may rotate a rotor shaft connected, e.g., to a generator to produce electricity.
- the combustion gases then exit the gas turbine via the exhaust section.
- the various components of the turbomachine endure various forms of wearing. Such wearing can lead to damage and/or failure of the individual components and the turbomachine in general.
- the compressor shaft and the turbine shaft which rotate during operation of the turbomachine, are susceptible to wearing.
- present compressor and turbine shafts may be expected to operate for approximately 144,000 hours and 5,000 starts.
- specific wear sensitive locations on the components such as the rabbet flanges, may tend to wear faster than other locations. These wear sensitive locations may limit the lives of the associated compressor shafts and/or turbine shafts.
- EP 3 130 749 relates to a patch ring for a compressor.
- EP 1 813 769 relates to an assembly with reduced radial dimensions between a turbine shaft and a compressor shaft journal in a turbomachine.
- a turbomachine is provided as set forth in claim 1.
- a method of servicing a turbomachine is provided as set forth in claim 8.
- upstream refers to the relative direction with respect to fluid flow in a fluid pathway.
- upstream refers to the direction from which the fluid flows
- downstream refers to the direction to which the fluid flows.
- radially refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component
- axially refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component
- the term “circumferentially” refers to the relative direction that extends around the axial centerline of a particular component.
- FIG. 1 illustrates a partial, cross-sectional view of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine 10.
- a gas turbine 10 which in the illustrated embodiment is a gas turbine 10.
- an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to a land-based and/or industrial gas turbine unless otherwise specified in the claims.
- the invention as described herein may be used in any type of turbomachine including but not limited to a steam turbine, an aircraft gas turbine, or a marine gas turbine.
- the gas turbine 10 as shown is cut-off at the turbine's centerline 12.
- the gas turbine 10 includes a compressor section 14, a combustor section 16 disposed downstream of the compressor section 14 and a turbine section 18 disposed downstream of the combustor section 16.
- the compressor section 14 may generally be configured to pressurize air flowing into the gas turbine 10. A portion of the pressurized air or working fluid then flows into the combustor section 16, wherein the air is mixed with fuel and combusted. Hot gases of combustion then flow through a transition piece 20 along an annular hot gas path to the turbine section 18 to drive the gas turbine 10 and generate power.
- the compressor section 14 may include an axial flow compressor 22 having a plurality of compressor stages characterized by alternating rows of rotor blades 24 and stator vanes 26.
- each compressor stage may include a row of circumferentially spaced rotor blades 24 mounted to a compressor rotor wheel 28 and a row of circumferentially spaced stator vanes 26 attached to a static compressor casing 30.
- the alternating rows of rotor blades 24 and stator vanes 26 may generally be configured to incrementally increase the pressure of the air flowing through the compressor 22 such that a desired increase in pressure is reached.
- the compressor rotor wheels 28, along with the rotor blades 24, generally comprise the rotating components of the compressor 22 and, thus, may form a compressor rotor assembly 32.
- the compressor rotor disks 28 may be stacked axially against one another about the turbine centerline 12 such that torque may be transmitted between the rotor disks 28.
- the combustion section 16 of the gas turbine 10 may generally include a plurality of combustors 34 (one of which is shown) disposed in an annular array about the turbine centerline 12.
- Each combustor 34 may generally be configured to receive a portion of the pressurized air discharged from the compressor 22, mix the air with fuel to form an air/fuel mixture and combust the mixture to produce hot gases of combustion. As indicated above, the hot gases of combustion may then flow from each combustor 34 through a transition piece 20 to the turbine section 18 of the gas turbine 10.
- the turbine section 18 may generally include a plurality of turbine stages characterized by alternating rows of turbine nozzles 36 and turbine buckets 38.
- each turbine stage may include a row of circumferentially spaced turbine nozzles 36 attached to a static turbine casing 40 and a row of circumferentially spaced turbine buckets 38 mounted to a turbine rotor wheel 42.
- the alternating rows of turbine nozzles 36 and buckets 38 may generally be configured to incrementally convert the energy of the hot gases of combustion into work manifested by rotation of the turbine rotor disks 42.
- the turbine rotor wheels 42, along with the turbine buckets 38, may generally comprise the rotating components of the turbine section 18 and, thus, may form a turbine rotor assembly 44.
- the turbine rotor wheels 42 may generally be stacked together axially along the turbine centerline 12.
- the turbine rotor wheels 42 may be spaced apart from one another by spacer wheels 46, with the rotor wheels 42 and spacer wheels 46 being stacked axially against one another such that torque may be transmitted between the rotor disks 42.
- Spacer wheels may additionally or alternatively space art the compressor rotor wheels 28.
- the gas turbine 10 may define an axial direction A and a circumferential direction C which extends around the axial direction A.
- the gas turbine 10 may also define a radial direction R perpendicular to the axial direction A.
- the gas turbine 10 may further include a compressor shaft 50 at least partially disposed within the compressor section 14 and a turbine shaft 52 at least partially disposed within the turbine section 18.
- the shafts 50, 52 may couple the compressor rotor assembly 32 and the turbine rotor assembly 44 together.
- the compressor shaft 50 may include an aft end 51 that couples to a forward end 53 of the turbine shaft 52.
- Each shaft 50, 52 may include one or more rabbets, e.g., a first rabbet 62 and a second rabbet 64.
- the first rabbet 62 may be annularly defined within the aft end 51 of the compressor shaft 51.
- the second rabbet 64 may be annularly defined within the forward end 53 of the turbine shaft 52.
- the compressor shaft 50 may extend from the compressor section 14, axially outward, and terminate at the first rabbet 62 defined within the aft end 51 of the compressor shaft 50.
- the turbine shaft 52 may extend from the turbine section 18, axially inward, and terminate at the second rabbet 64 defined within the forward end 53 of the turbine shaft 52.
- the rabbets 62, 64 may form a marriage joint 58, which functions to couple the compressor rotor assembly 32 to the turbine rotor assembly 44 and maintain coaxial alignment between the compressor shaft 50 and the turbine shaft 52.
- FIG. 2 illustrates a cross-sectional view of a shaft assembly 60, prior to having service maintenance performed thereon and the installation of a patch ring 100 therein (as shown in FIG. 3 through 11).
- the shaft assembly 60 shown in FIG. 2 may be before or after operation of the gas turbine 10.
- the shaft assembly 60 may include a compressor shaft 50 coupled to a turbine shaft 52 to form a marriage joint 58 therebetween.
- the compressor shaft 50 may include a first pre-machined rabbet 54.
- the turbine shaft 52 may include a second pre-machined rabbet 56 opposite the first pre-machined rabbet 54.
- the first pre-machined rabbet 54 may include a first axially extending face 55
- the second pre-machined rabbet 56 may include a second axially extending face 57.
- the first axially extending face 55 of the first pre-machined rabbet 54 is in direct contact with the second axially extending face 57 of the second pre-machined rabbet 56.
- the turbine shaft 50 is disconnected from the compressor shaft 52 and inspected.
- the turbine shaft 50 and the compressor shaft 52 may become damaged during this process, and this damage may be from operational wear and tear or from the actual disassembly process itself.
- the first rabbet 62 and the second rabbet 64 ( FIG. 1 ) are common places for this damage to occur.
- FIGS. 3 and 4 illustrate enlarged cross-sectional views of shaft assemblies 60 with the patch ring 100 in position, e.g. after servicing of the gas turbine 10, in accordance with embodiments of the present disclosure.
- the shaft assemblies 60 may each include a compressor shaft 50, a turbine shaft 52 coupled to the compressor shaft 50, and a marriage joint 58 defined therebetween.
- the compressor shaft 50 may include first rabbet 62 annularly defined within the compressor shaft 50.
- the turbine shaft 52 may include a second rabbet 64 annularly defined within the turbine shaft 52.
- the first rabbet 62 and the second rabbet 64 may be machined within the shafts 50, 52 in the circumferential direction C.
- a patch ring 100 may be disposed between the first rabbet 62 of the compressor shaft 50 and the second rabbet 64 of the turbine shaft 52.
- the first rabbet 62 may be positioned opposite the second rabbet 64.
- the first rabbet 62 of the compressor shaft 50 may be disposed radially inward the second rabbet 64 of the turbine shaft 52.
- the first rabbet 62 of the compressor shaft 50 may be disposed radially outward the second rabbet 64 of the turbine shaft 52.
- the first rabbet 62 may include a first axially extending face 66 and a first radially extending face 68.
- the second rabbet 64 may include a second axially extending face 70 and a second radially extending face 72.
- the axially extending faces 66, 70 and radially extending faces 68, 72 may be substantially flat surfaces.
- the axially extending faces 66, 70 and radially extending faces 68, 72 may be the outermost surfaces of the rabbets 62, 64.
- axially extending refers to a component and/or surface extending along the relative direction that is substantially parallel and/or coaxially aligned to the axial direction A of gas turbine 10.
- radially extending refers to a component and/or surface extending along the relative direction that is substantially perpendicular to the axial direction A of gas turbine 10.
- the first axially extending face 66 may be radially spaced apart from the second axially extending face 72, and the patch ring 100 may be positioned therebetween.
- the patch ring 100 may be mounted between the first rabbet 62 and second rabbet 64 to advantageously provide the design-required interference between the first axially extending face 66 and the second axially extending face 72.
- the patch ring 100 may also reduce or prevent damaging axial movement between the axially extending faces 66, 72 during operation of the gas turbine 10.
- the first rabbet 62 and second rabbet 64 may axially overlap with one another.
- the first radially extending face 68 of the first rabbet 62 may extend axially beyond the second radially extending face 72 of the second rabbet 64.
- the first radially extending face 68 may extend axially outward and beyond the second radially extending face 72.
- the first axially extending face 66 may face towards, overlap with, and/or be parallel to, the second axially extending face 70.
- Patch ring 100 includes a main body 102 a first arm 104 and a second arm 106.
- the main body 102 of patch ring 100 may be positioned radially between the first axially extending face 66 of the compressor shaft 50 and the second axially extending face 70 of the turbine shaft 52.
- the main body 102 of patch ring 100 may function to radially space apart the first axially extending face 66 of the first rabbet 62 from the second axially extending face 70 of the second rabbet 64 to provide proper alignment between the compressor shaft 50 and the turbine shaft 52.
- the main body 102 is in direct contact with both the first axially extending face 66 and the second axially extending face 70.
- the first arm 104 and the second arm 106 extend radially away from the main body 102.
- the first arm 104 extends radially outward from the main body 102 of patch ring 100
- the second arm 106 extends radially inward the main body of patch ring 100.
- the first arm 104 may extend radially outwardly from the main body 102, beyond the second axially extending face 70, and at least partially along the second radially extending face 72.
- the second arm 104 extends radially inwardly from the main body 102, beyond the first axially extending face 66, and at least partially along the first radially extending face 68.
- the first arm 104 and the second arm 106 may be in direct contact with the second rabbet 64 and first rabbet 62 respectively.
- the first arm 104 may be axially spaced apart from the second arm 106, i.e., positioned on opposite sides of the main body.
- the first arm 104 and second arm 106 may extend in opposite radial directions to one another, and on opposite axial sides of the main body 102, to form a generally "S" like shape.
- the first arm 104 and second arm 106 may each include a support surface 108, 110, as shown.
- the support surface 108 of the first arm 104 may be a substantially flat surface in direct contact with the second radially extending face 72.
- the support surface 110 of the second arm 106 may be a substantially flat surface in direct contact with the first radially extending face 68.
- the support surface 108 of the first arm and support surface 110 of the second arm 106 may be substantially flat surfaces that directly abut the second radially extending face 72 and first radially extending face 68, respectively.
- the support surfaces 108, 110 of the arms 104, 106 may function to prohibit movement and/or sliding of the patch ring 100 within the marriage joint 58.
- the first arm 104 and second arm 106 may each also include an exterior surface 112, 114.
- the exterior surface 112 of the first arm may be located axially inward of the support surface 108.
- the exterior surface 114 of the second arm may be located axially outward of the support surface 110.
- the exterior surfaces 112, 114 may be longer than the support surfaces 108, 110 in the radial direction.
- the first rabbet 62 of the compressor shaft 50 and the second rabbet 64 of the turbine shaft 52 may each further include an outer surface 116, 118.
- the outer surfaces 116, 118 may be a substantially arcuate exterior surfaces that are axially spaced from the radially extending faces 68, 72 to define gaps 120, 122 therebetween.
- the outer surface 116 of the first rabbet 62 may be disposed axially inward the second radially extending face 72 and may define a gap 120 therebetween.
- the outer surface 118 of the second rabbet 64 may be disposed axially outward the second radially extending face 72 and may define a gap 122 therebetween.
- the first rabbet 62 may at least partially extend into the second gap 122
- the second rabbet 64 may at least partially extend into the first gap 120.
- the first arm 104 of the patch ring 100 may extend at least partially into the gap 120, and the second arm 106 may extend at least partially into the gap 122.
- the gaps 120, 122 may function to create axial space between the first arm 104 and the second arm 106 in order to allow for thermal expansion during operation of the gas turbine 10.
- the exterior surfaces 112, 114 may advantageously act as an intermediary surface that prevents the outer surfaces 116, 118 from contacting the radially extending faces 68, 72 due to thermal expansion during operation of the gas turbine 10.
- FIG. 4 illustrates another embodiment of a patch ring 100.
- the first arm 104 may be coaxially aligned with the second arm 106, i.e., positioned the same side of the main body 102 and sharing the same axial centerline.
- the first arm 104 and second arm 106 may extend in opposite radial directions to one another to form a generally "T" like shape.
- the second rabbet 64 may further include a radial cutout 212 sized to receive the first arm 104 of the patch ring 100 therein.
- the radial cutout 212 may function to restrict the axial movement of the patch ring 100 within the marriage joint 58.
- the first arm 104 may be positioned axially between, and in contact with, the support surface 108 and the outer surface 118 during operation of the gas turbine 10, thereby restricting the axial movement of patch ring 100 within marriage joint 58.
- the radial cutout 212 may further include a cutout support surface 214.
- the first arm 104 and second arm 106 may each include a support surface 108, 110, as shown.
- the support surface 108 of the first arm 104 may a substantially flat surface in that directly abuts the cutout support surface 214.
- the support surface 110 of the second arm 106 may be a substantially flat surface that directly abuts the first radially extending face 68.
- the support surfaces 108, 110 of the arms 104, 106 may function to prohibit movement and/or sliding of the patch ring 100 within the marriage joint 58.
- FIGS. 5 and 6 illustrate various views of patch ring 100, in accordance with embodiments of the present disclosure.
- the first arm 104 and the second arm 106 may each be one continuous annular member that extend in the circumferential direction.
- the first arm 104 and the second arm 106 may be defined along the circumferential direction.
- the first arm 104 may be a plurality of first arms 104' that are spaced apart from one another along the main body 102 in the circumferential direction C.
- the second arm 106 may be a plurality of second arms 106' that are spaced apart from one another along the main body 102 in the circumferential direction C.
- the patch ring 100 may also include one or more grooves 124 disposed circumferentially between the plurality of first arms 104' and/or the plurality of second arms 106'.
- the grooves 124 may extend radially into the main body 102 of patch ring 100 and function as a passageway for cooling air from the compressor to flow therethrough.
- air from the compressor section 14 may purge stagnant air from the various cavities and crevices of the first rabbet 62 of the compressor shaft 50, the second rabbet 64 of the turbine shaft 52, and the patch ring 100.
- FIG. 9 provides a flow chart which graphically illustrates a method 300 of servicing a turbomachine, such as the gas turbine 10 described herein, in accordance with one or more additional example embodiments of the present disclosure.
- the method 300 may include a step 302 of machining a first rabbet 62 within an aft end 51 of a compressor shaft, such step may occur, of example, after initial operation of gas turbine 10.
- the first rabbet 62 may include a first axially extending face 66 and a first radially extending face 68. Further, the first rabbet may be annularly defined within the aft end 51 of the compressor shaft 50.
- the method 300 may further include a step 304 of machining a second rabbet 64 within a forward end 53 of a turbine shaft 52.
- the second rabbet 64 may include a second axially extending face 70 and a second radially extending face 72. Further, the second rabbet 64 may be annularly defined within the forward end 53 of the turbine shaft 52 and positioned opposite the first rabbet 62.
- the method 300 may also include a step 306 of installing a patch ring radially between the first rabbet 62 and the second rabbet 64.
- the main body 102 of patch ring 100 may function to provide the design-intended interference between the first axially extending face 66 and second axially extending face 70, even after the surfaces have undergone servicing and/or machining.
- the pre-machined rabbets 54, 56 shown in FIG. 2 may be subjected to wear during operation of gas turbine 10 that requires the various surfaces of the pre-machined rabbets 54, 56, e.g. the axially extending faces 55, 57, to be serviced to restore the required interference.
- the patch ring 100 provides the required interference between the rabbets 62, 64 (or post-machined rabbets) after the gas turbine 10 has been serviced.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- The present disclosure relates generally to improved patch rings and associated methods. In particular, the invention relates to improved patch rings for use in turbomachine marriage joints.
- Turbomachines are utilized in a variety of industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section progressively increases the pressure of a working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and a fuel (e.g., natural gas) mix within the combustion section and burn in a combustion chamber to generate high pressure and high temperature combustion gases. The combustion gases flow from the combustion section into the turbine section where they expand to produce work. For example, expansion of the combustion gases in the turbine section may rotate a rotor shaft connected, e.g., to a generator to produce electricity. The combustion gases then exit the gas turbine via the exhaust section.
- During operation of a turbomachine, the various components of the turbomachine endure various forms of wearing. Such wearing can lead to damage and/or failure of the individual components and the turbomachine in general. In particular, the compressor shaft and the turbine shaft, which rotate during operation of the turbomachine, are susceptible to wearing. For example, present compressor and turbine shafts may be expected to operate for approximately 144,000 hours and 5,000 starts. Further, in many cases, specific wear sensitive locations on the components, such as the rabbet flanges, may tend to wear faster than other locations. These wear sensitive locations may limit the lives of the associated compressor shafts and/or turbine shafts.
- Defects in the compressor shaft and turbine shaft must be repaired so they maintain design intent. Currently, the compressor shaft and turbine shaft are repaired by post-operational machining on the contact surface defined between the shafts, in order to restore the design-specified interference between the two shafts. However, over multiple service intervals, machining the rabbet joint can negatively impact the desired contact interference between the compressor shaft and turbine shaft.
- Accordingly, improved methods and apparatuses for repairing turbomachine joints is desired in the art. In particular, improved methods and apparatuses for repairing a rabbet joint between a compressor shaft and a turbine shaft is desired.
-
EP 3 130 749 relates to a patch ring for a compressor.EP 1 813 769 relates to an assembly with reduced radial dimensions between a turbine shaft and a compressor shaft journal in a turbomachine. - Aspects and advantages of the shaft assemblies, turbomachines, and methods of servicing a turbomachine in accordance with the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the technology. The invention is defined by the claims.
- In accordance with one aspect of the invention, a turbomachine is provided as set forth in claim 1.
- In accordance with another aspect, a method of servicing a turbomachine is provided as set forth in claim 8.
- These and other features, aspects and advantages of the present shaft assemblies, turbomachines, and methods of servicing a turbomachine will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the technology and, together with the description, serve to explain the principles of the technology.
- A full and enabling disclosure of the present shaft assemblies, turbomachines, and methods of servicing a turbomachine, including the best mode of making and using the present systems and methods, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:
-
FIG. 1 is a schematic illustration of a turbomachine in accordance with embodiments of the present disclosure; -
FIG. 2 illustrates a cross-sectional view of a shaft assembly prior to the installation of a patch ring in accordance with embodiments of the present disclosure; -
FIG. 3 illustrates a cross sectional view of a shaft assembly showing a patch ring positioned therein in accordance with embodiments of the present disclosure; -
FIG. 4 illustrates a cross sectional view of a shaft assembly showing a patch ring positioned therein in accordance with embodiments of the present disclosure; -
FIG. 5 illustrates a side view of a patch ring in accordance with embodiments of the present disclosure; -
FIG. 6 illustrates an enlarged perspective view of the patch ring shown inFIG. 5 in accordance with embodiments of the present disclosure; -
FIG. 7 illustrates a side view of a patch ring in accordance with embodiments of the present disclosure. -
FIG. 8 illustrates an enlarged perspective view of the patch ring shown inFIG. 7 in accordance with embodiments of the present disclosure; -
FIG. 9 illustrates a method of servicing a turbomachine in accordance with embodiments of the present disclosure. - Reference now will be made in detail to embodiments of the present shaft assemblies, turbomachines, and methods of servicing a turbomachine, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation, rather than limitation of, the technology. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present technology without departing from the scope of the claimed technology. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims.
- The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.
- As used herein, the terms "upstream" (or "forward") and "downstream" (or "aft") refer to the relative direction with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction to which the fluid flows. The term "radially" refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term "axially" refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component and the term "circumferentially" refers to the relative direction that extends around the axial centerline of a particular component. terms of approximation, such as "generally," or "about" include values within ten percent greater or less than the stated value. When used in the context of an angle or direction, such terms include within ten degrees greater or less than the stated angle or direction. For example, "generally vertical" includes directions within ten degrees of vertical in any direction, e.g., clockwise or counter-clockwise.
- Referring now to the drawings,
FIG. 1 illustrates a partial, cross-sectional view of one embodiment of a turbomachine, which in the illustrated embodiment is agas turbine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to a land-based and/or industrial gas turbine unless otherwise specified in the claims. For example, the invention as described herein may be used in any type of turbomachine including but not limited to a steam turbine, an aircraft gas turbine, or a marine gas turbine. - As shown, the
gas turbine 10 as shown is cut-off at the turbine'scenterline 12. As shown, thegas turbine 10 includes acompressor section 14, acombustor section 16 disposed downstream of thecompressor section 14 and aturbine section 18 disposed downstream of thecombustor section 16. Thecompressor section 14 may generally be configured to pressurize air flowing into thegas turbine 10. A portion of the pressurized air or working fluid then flows into thecombustor section 16, wherein the air is mixed with fuel and combusted. Hot gases of combustion then flow through atransition piece 20 along an annular hot gas path to theturbine section 18 to drive thegas turbine 10 and generate power. - In several embodiments, the
compressor section 14 may include anaxial flow compressor 22 having a plurality of compressor stages characterized by alternating rows ofrotor blades 24 andstator vanes 26. Specifically, each compressor stage may include a row of circumferentially spacedrotor blades 24 mounted to acompressor rotor wheel 28 and a row of circumferentially spacedstator vanes 26 attached to astatic compressor casing 30. The alternating rows ofrotor blades 24 andstator vanes 26 may generally be configured to incrementally increase the pressure of the air flowing through thecompressor 22 such that a desired increase in pressure is reached. Thecompressor rotor wheels 28, along with therotor blades 24, generally comprise the rotating components of thecompressor 22 and, thus, may form acompressor rotor assembly 32. For example, in several embodiments, thecompressor rotor disks 28 may be stacked axially against one another about theturbine centerline 12 such that torque may be transmitted between therotor disks 28. - The
combustion section 16 of thegas turbine 10 may generally include a plurality of combustors 34 (one of which is shown) disposed in an annular array about theturbine centerline 12. Eachcombustor 34 may generally be configured to receive a portion of the pressurized air discharged from thecompressor 22, mix the air with fuel to form an air/fuel mixture and combust the mixture to produce hot gases of combustion. As indicated above, the hot gases of combustion may then flow from each combustor 34 through atransition piece 20 to theturbine section 18 of thegas turbine 10. - The
turbine section 18 may generally include a plurality of turbine stages characterized by alternating rows ofturbine nozzles 36 andturbine buckets 38. In particular, each turbine stage may include a row of circumferentially spacedturbine nozzles 36 attached to astatic turbine casing 40 and a row of circumferentially spacedturbine buckets 38 mounted to aturbine rotor wheel 42. The alternating rows ofturbine nozzles 36 andbuckets 38 may generally be configured to incrementally convert the energy of the hot gases of combustion into work manifested by rotation of theturbine rotor disks 42. Theturbine rotor wheels 42, along with theturbine buckets 38, may generally comprise the rotating components of theturbine section 18 and, thus, may form aturbine rotor assembly 44. Similar to thecompressor rotor wheels 28, theturbine rotor wheels 42 may generally be stacked together axially along theturbine centerline 12. For example, as shown inFIG. 1 , theturbine rotor wheels 42 may be spaced apart from one another byspacer wheels 46, with therotor wheels 42 andspacer wheels 46 being stacked axially against one another such that torque may be transmitted between therotor disks 42. Spacer wheels may additionally or alternatively space art thecompressor rotor wheels 28. - As shown in
FIG. 1 , thegas turbine 10 may define an axial direction A and a circumferential direction C which extends around the axial direction A. Thegas turbine 10 may also define a radial direction R perpendicular to the axial direction A. - As further shown in
FIG. 1 , and referring also toFIG. 2 , thegas turbine 10 may further include acompressor shaft 50 at least partially disposed within thecompressor section 14 and aturbine shaft 52 at least partially disposed within theturbine section 18. Theshafts compressor rotor assembly 32 and theturbine rotor assembly 44 together. As shown, thecompressor shaft 50 may include anaft end 51 that couples to aforward end 53 of theturbine shaft 52. Eachshaft first rabbet 62 and asecond rabbet 64. Thefirst rabbet 62 may be annularly defined within theaft end 51 of thecompressor shaft 51. Similarly, thesecond rabbet 64 may be annularly defined within theforward end 53 of theturbine shaft 52. In many embodiments, thecompressor shaft 50 may extend from thecompressor section 14, axially outward, and terminate at thefirst rabbet 62 defined within theaft end 51 of thecompressor shaft 50. Likewise, theturbine shaft 52 may extend from theturbine section 18, axially inward, and terminate at thesecond rabbet 64 defined within theforward end 53 of theturbine shaft 52. Therabbets compressor rotor assembly 32 to theturbine rotor assembly 44 and maintain coaxial alignment between thecompressor shaft 50 and theturbine shaft 52. -
FIG. 2 illustrates a cross-sectional view of ashaft assembly 60, prior to having service maintenance performed thereon and the installation of apatch ring 100 therein (as shown inFIG. 3 through 11). In various embodiments, theshaft assembly 60 shown inFIG. 2 may be before or after operation of thegas turbine 10. As shown, theshaft assembly 60 may include acompressor shaft 50 coupled to aturbine shaft 52 to form a marriage joint 58 therebetween. As shown, thecompressor shaft 50 may include a firstpre-machined rabbet 54. Likewise, theturbine shaft 52 may include a secondpre-machined rabbet 56 opposite the firstpre-machined rabbet 54. The firstpre-machined rabbet 54 may include a firstaxially extending face 55, and the secondpre-machined rabbet 56 may include a secondaxially extending face 57. As shown, prior to installation of apatch ring 100, the first axially extendingface 55 of the firstpre-machined rabbet 54 is in direct contact with the second axially extendingface 57 of the secondpre-machined rabbet 56. - During disassembly of the turbomachine for service or repair, the
turbine shaft 50 is disconnected from thecompressor shaft 52 and inspected. Theturbine shaft 50 and thecompressor shaft 52 may become damaged during this process, and this damage may be from operational wear and tear or from the actual disassembly process itself. Thefirst rabbet 62 and the second rabbet 64 (FIG. 1 ) are common places for this damage to occur. -
FIGS. 3 and4 illustrate enlarged cross-sectional views ofshaft assemblies 60 with thepatch ring 100 in position, e.g. after servicing of thegas turbine 10, in accordance with embodiments of the present disclosure. As shown, theshaft assemblies 60 may each include acompressor shaft 50, aturbine shaft 52 coupled to thecompressor shaft 50, and a marriage joint 58 defined therebetween. Thecompressor shaft 50 may includefirst rabbet 62 annularly defined within thecompressor shaft 50. Likewise, theturbine shaft 52 may include asecond rabbet 64 annularly defined within theturbine shaft 52. For example, thefirst rabbet 62 and thesecond rabbet 64 may be machined within theshafts patch ring 100 may be disposed between thefirst rabbet 62 of thecompressor shaft 50 and thesecond rabbet 64 of theturbine shaft 52. - In many embodiments, the
first rabbet 62 may be positioned opposite thesecond rabbet 64. For example, in the embodiment shown inFIGS. 3 and4 , thefirst rabbet 62 of thecompressor shaft 50 may be disposed radially inward thesecond rabbet 64 of theturbine shaft 52. However, in other embodiments (not shown), thefirst rabbet 62 of thecompressor shaft 50 may be disposed radially outward thesecond rabbet 64 of theturbine shaft 52. - As shown in
FIGS. 3 and4 , thefirst rabbet 62 may include a firstaxially extending face 66 and a firstradially extending face 68. Likewise, thesecond rabbet 64 may include a secondaxially extending face 70 and a secondradially extending face 72. As shown inFIGS. 3 and4 , the axially extending faces 66, 70 and radially extending faces 68, 72 may be substantially flat surfaces. Further, as shown, the axially extending faces 66, 70 and radially extending faces 68, 72 may be the outermost surfaces of therabbets - As used herein, "axially extending" refers to a component and/or surface extending along the relative direction that is substantially parallel and/or coaxially aligned to the axial direction A of
gas turbine 10. Similarly, "radially extending" refers to a component and/or surface extending along the relative direction that is substantially perpendicular to the axial direction A ofgas turbine 10. - As shown, the first axially extending
face 66 may be radially spaced apart from the second axially extendingface 72, and thepatch ring 100 may be positioned therebetween. In some embodiments, thepatch ring 100 may be mounted between thefirst rabbet 62 andsecond rabbet 64 to advantageously provide the design-required interference between the first axially extendingface 66 and the second axially extendingface 72. Further, thepatch ring 100 may also reduce or prevent damaging axial movement between the axially extending faces 66, 72 during operation of thegas turbine 10. - In many embodiments, as shown in
FIGS. 3 and4 , thefirst rabbet 62 andsecond rabbet 64 may axially overlap with one another. For example, the first radially extendingface 68 of thefirst rabbet 62 may extend axially beyond the second radially extendingface 72 of thesecond rabbet 64. Specifically, the first radially extendingface 68 may extend axially outward and beyond the second radially extendingface 72. In such embodiments, the first axially extendingface 66 may face towards, overlap with, and/or be parallel to, the second axially extendingface 70. -
Patch ring 100 includes a main body 102 afirst arm 104 and asecond arm 106. In the embodiments shown inFIG. 3 and4 , themain body 102 ofpatch ring 100 may be positioned radially between the first axially extendingface 66 of thecompressor shaft 50 and the second axially extendingface 70 of theturbine shaft 52. For example, themain body 102 ofpatch ring 100 may function to radially space apart the first axially extendingface 66 of thefirst rabbet 62 from the second axially extendingface 70 of thesecond rabbet 64 to provide proper alignment between thecompressor shaft 50 and theturbine shaft 52. As shown inFIGS. 3 and4 , themain body 102 is in direct contact with both the first axially extendingface 66 and the second axially extendingface 70. - As shown in
FIG. 3 , thefirst arm 104 and thesecond arm 106 extend radially away from themain body 102. Thefirst arm 104 extends radially outward from themain body 102 ofpatch ring 100, and thesecond arm 106 extends radially inward the main body ofpatch ring 100. As shown inFIG. 3 , thefirst arm 104 may extend radially outwardly from themain body 102, beyond the second axially extendingface 70, and at least partially along the second radially extendingface 72. Similarly, thesecond arm 104 extends radially inwardly from themain body 102, beyond the first axially extendingface 66, and at least partially along the first radially extendingface 68. In many embodiments, thefirst arm 104 and thesecond arm 106 may be in direct contact with thesecond rabbet 64 andfirst rabbet 62 respectively. - As shown in
FIG. 3 , thefirst arm 104 may be axially spaced apart from thesecond arm 106, i.e., positioned on opposite sides of the main body. In some embodiments, thefirst arm 104 andsecond arm 106 may extend in opposite radial directions to one another, and on opposite axial sides of themain body 102, to form a generally "S" like shape. - The
first arm 104 andsecond arm 106 may each include asupport surface support surface 108 of thefirst arm 104 may be a substantially flat surface in direct contact with the second radially extendingface 72. Similarly, thesupport surface 110 of thesecond arm 106 may be a substantially flat surface in direct contact with the first radially extendingface 68. For example, thesupport surface 108 of the first arm andsupport surface 110 of thesecond arm 106 may be substantially flat surfaces that directly abut the second radially extendingface 72 and first radially extendingface 68, respectively. The support surfaces 108, 110 of thearms patch ring 100 within the marriage joint 58. - As shown in
FIG. 3 , thefirst arm 104 andsecond arm 106 may each also include anexterior surface exterior surface 112 of the first arm may be located axially inward of thesupport surface 108. Similarly, theexterior surface 114 of the second arm may be located axially outward of thesupport surface 110. As shown, theexterior surfaces - As shown in
FIGS. 3 and4 , thefirst rabbet 62 of thecompressor shaft 50 and thesecond rabbet 64 of theturbine shaft 52 may each further include anouter surface outer surfaces gaps outer surface 116 of thefirst rabbet 62 may be disposed axially inward the second radially extendingface 72 and may define agap 120 therebetween. Similarly, theouter surface 118 of thesecond rabbet 64 may be disposed axially outward the second radially extendingface 72 and may define agap 122 therebetween. In many embodiments thefirst rabbet 62 may at least partially extend into thesecond gap 122, and thesecond rabbet 64 may at least partially extend into thefirst gap 120. - In the embodiment shown in
FIG. 3 , thefirst arm 104 of thepatch ring 100 may extend at least partially into thegap 120, and thesecond arm 106 may extend at least partially into thegap 122. Thegaps first arm 104 and thesecond arm 106 in order to allow for thermal expansion during operation of thegas turbine 10. The exterior surfaces 112, 114 may advantageously act as an intermediary surface that prevents theouter surfaces gas turbine 10. -
FIG. 4 illustrates another embodiment of apatch ring 100. As shown, thefirst arm 104 may be coaxially aligned with thesecond arm 106, i.e., positioned the same side of themain body 102 and sharing the same axial centerline. In some embodiments, thefirst arm 104 andsecond arm 106 may extend in opposite radial directions to one another to form a generally "T" like shape. - In the embodiment shown in
FIG. 4 , thesecond rabbet 64 may further include aradial cutout 212 sized to receive thefirst arm 104 of thepatch ring 100 therein. Theradial cutout 212 may function to restrict the axial movement of thepatch ring 100 within the marriage joint 58. For example, thefirst arm 104 may be positioned axially between, and in contact with, thesupport surface 108 and theouter surface 118 during operation of thegas turbine 10, thereby restricting the axial movement ofpatch ring 100 within marriage joint 58. As shown, theradial cutout 212 may further include acutout support surface 214. Thefirst arm 104 andsecond arm 106 may each include asupport surface support surface 108 of thefirst arm 104 may a substantially flat surface in that directly abuts thecutout support surface 214. Similarly, thesupport surface 110 of thesecond arm 106 may be a substantially flat surface that directly abuts the first radially extendingface 68. The support surfaces 108, 110 of thearms patch ring 100 within the marriage joint 58. -
FIGS. 5 and 6 illustrate various views ofpatch ring 100, in accordance with embodiments of the present disclosure. As shown, thefirst arm 104 and thesecond arm 106 may each be one continuous annular member that extend in the circumferential direction. Thefirst arm 104 and thesecond arm 106 may be defined along the circumferential direction. - Alternatively, as shown in
FIGS. 7 and 8 , thefirst arm 104 may be a plurality of first arms 104' that are spaced apart from one another along themain body 102 in the circumferential direction C. Likewise, as shown, thesecond arm 106 may be a plurality of second arms 106' that are spaced apart from one another along themain body 102 in the circumferential direction C. - As shown in
FIGS. 7 and 8 , thepatch ring 100 may also include one ormore grooves 124 disposed circumferentially between the plurality of first arms 104' and/or the plurality of second arms 106'. Thegrooves 124 may extend radially into themain body 102 ofpatch ring 100 and function as a passageway for cooling air from the compressor to flow therethrough. For example, air from thecompressor section 14 may purge stagnant air from the various cavities and crevices of thefirst rabbet 62 of thecompressor shaft 50, thesecond rabbet 64 of theturbine shaft 52, and thepatch ring 100. -
FIG. 9 provides a flow chart which graphically illustrates amethod 300 of servicing a turbomachine, such as thegas turbine 10 described herein, in accordance with one or more additional example embodiments of the present disclosure. As illustrated inFIG. 9 , themethod 300 may include astep 302 of machining afirst rabbet 62 within anaft end 51 of a compressor shaft, such step may occur, of example, after initial operation ofgas turbine 10. Thefirst rabbet 62 may include a firstaxially extending face 66 and a firstradially extending face 68. Further, the first rabbet may be annularly defined within theaft end 51 of thecompressor shaft 50. Themethod 300 may further include astep 304 of machining asecond rabbet 64 within aforward end 53 of aturbine shaft 52. Thesecond rabbet 64 may include a secondaxially extending face 70 and a secondradially extending face 72. Further, thesecond rabbet 64 may be annularly defined within theforward end 53 of theturbine shaft 52 and positioned opposite thefirst rabbet 62. Themethod 300 may also include astep 306 of installing a patch ring radially between thefirst rabbet 62 and thesecond rabbet 64. - During operation of the
gas turbine 10, themain body 102 ofpatch ring 100 may function to provide the design-intended interference between the first axially extendingface 66 and second axially extendingface 70, even after the surfaces have undergone servicing and/or machining. For example, thepre-machined rabbets FIG. 2 may be subjected to wear during operation ofgas turbine 10 that requires the various surfaces of thepre-machined rabbets patch ring 100 provides the required interference between therabbets 62, 64 (or post-machined rabbets) after thegas turbine 10 has been serviced. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the appended claims.
Claims (11)
- A turbomachine (10), comprising:a compressor section (14);a combustor section (16);a turbine section (18);a compressor shaft (50) at least partially disposed in the compressor section (14), the compressor shaft (50) having a first rabbet (62) annularly defined therein, the first rabbet (62) including a first axially extending face (55, 66) and a first radially extending face (68);a turbine shaft (52) at least partially disposed in the turbine section (18) and coupled to the compressor shaft (50), the turbine shaft (52) having a second rabbet (64) annularly defined therein and positioned opposite the first rabbet (62), the second rabbet (64) including a second axially extending face (57, 70) and a second radially extending face (72); anda patch ring (100) mounted between the first rabbet (62) and the second rabbet (64), wherein the patch ring (100) includes a main body (102), a first arm (104) extending radially outward from the main body (102), and a second arm (106) extending radially inward from the main body (102),wherein the main body (102) of the patch ring (100) contacts the first axially extending face (55) of the compressor shaft (50) and the second axially extending face (57) of the turbine shaft (52).
- The turbomachine as in claim 1, wherein the first arm (104) and the second arm (106) of the patch ring (100) are axially spaced from one another.
- The turbomachine as in claim 1, wherein the first arm (104) and the second arm (106) of the patch ring (100) are coaxially aligned with one another.
- The turbomachine as in claim 1, wherein the main body (102) of the patch ring (100) is positioned radially between the first axially extending face (55) and the second axially extending face (57).
- The turbomachine as in claim 2, wherein the first rabbet (62) of the compressor shaft (50) and the second rabbet (64) of the turbine shaft (52) each comprise an outer surface (116, 118), the outer surface (116) of the first rabbet (62) is disposed axially inward of the second radially extending face (72) of the second rabbet (64), and the outer surface (118) of the second rabbet (64) is disposed axially outward of the first radially extending face (68) of the first rabbet (62).
- The turbomachine as in claim 2, wherein the first arm (104) of the patch ring (100) contacts the second radially extending face (72) of the second rabbet (64) and the second arm (106) of the patch ring (100) contacts the first radially extending face (68) of the first rabbet (62).
- The turbomachine as in claim 5, wherein a first gap (120) is defined axially between the first arm (104) of the patch ring (100) and the outer surface (116) of the first rabbet (62), and a second gap (122) is defined axially between the second arm (106) of the patch ring (100) and outer surface (118) of the second rabbet (64).
- A method of servicing a turbomachine, the method comprising:machining a first rabbet (62) within an aft end of a compressor shaft (50), wherein the first rabbet (62) includes a first axially extending face (55) and a first radially extending face (68), and wherein the first rabbet (62) is annularly defined within the aft end of the compressor shaft (50);machining a second rabbet (64) within a forward end of a turbine shaft (52), wherein the second rabbet (64) includes a second axially extending face (57) and a second radially extending face (72), and wherein the second rabbet (64) is annularly defined within the forward end of the turbine shaft (52) and positioned opposite the first rabbet (62); andinstalling a patch ring (100) between the first rabbet (62) and the second rabbet (64), wherein the patch ring (100) includes a main body (102), a first arm (104) extending radially outward from the main body (102), and a second arm (106) extending radially inward from the main body (102),wherein the main body (102) of the patch ring (100) contacts the first axially extending face (55) of the compressor shaft (50) and the second axially extending face (57) of the turbine shaft (52).
- The method as in claim 8, wherein the first arm (104) is axially spaced from the second arm (106).
- The method as in claim 8, wherein the main body (102) of the patch ring (100) is positioned between the compressor shaft (50) and the turbine shaft (52).
- The method as in claim 9, wherein the first arm (104) of the patch ring (100) contacts the second radially extending face (72) of the second rabbet (64) and the second arm (106) of the patch ring (100) contacts the first radially extending face (68) of first rabbet (62).
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US16/724,852 US11174735B2 (en) | 2019-12-23 | 2019-12-23 | Patch rings and methods of use |
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EP3842618A1 EP3842618A1 (en) | 2021-06-30 |
EP3842618B1 true EP3842618B1 (en) | 2023-05-03 |
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EP20212534.0A Active EP3842618B1 (en) | 2019-12-23 | 2020-12-08 | Improved patch rings and methods of use |
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US (1) | US11174735B2 (en) |
EP (1) | EP3842618B1 (en) |
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Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
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EP1813769B1 (en) * | 2006-01-27 | 2009-03-25 | Snecma | Assembly with reduced radial dimensions between a turbine shaft and a compressor shaft journal in a turbomachine |
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CH257836A (en) * | 1947-08-07 | 1948-10-31 | Sulzer Ag | Rotors for centrifugal machines, in particular for gas turbines. |
US3713676A (en) * | 1971-05-07 | 1973-01-30 | Gen Electric | Predeformed rabbit joint |
CH590414A5 (en) * | 1975-07-04 | 1977-08-15 | Bbc Brown Boveri & Cie | |
US9909595B2 (en) * | 2015-07-21 | 2018-03-06 | General Electric Company | Patch ring for a compressor |
GB201806432D0 (en) * | 2018-04-20 | 2018-06-06 | Rolls Royce Plc | A shaft assembly |
FR3085409B1 (en) * | 2018-08-29 | 2020-12-11 | Safran Aircraft Engines | COUPLING FOR TURBOMACHINE TYPE CURVIC WITH LOCKING |
-
2019
- 2019-12-23 US US16/724,852 patent/US11174735B2/en active Active
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2020
- 2020-11-24 CN CN202011333328.7A patent/CN113090333A/en active Pending
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Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
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EP1813769B1 (en) * | 2006-01-27 | 2009-03-25 | Snecma | Assembly with reduced radial dimensions between a turbine shaft and a compressor shaft journal in a turbomachine |
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JP2021099097A (en) | 2021-07-01 |
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US20210189899A1 (en) | 2021-06-24 |
CN113090333A (en) | 2021-07-09 |
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